Aeronautics and astronautics – Aircraft control – Automatic
Patent
1991-08-27
1994-05-24
Huppert, Michael S.
Aeronautics and astronautics
Aircraft control
Automatic
244 1713, 244195, 36443107, B64C 1144, G05D 100
Patent
active
053141474
ABSTRACT:
A helicopter engine speed reference (66) is increased (117,118) in response to heavy rotor loading (102) in excess of a threshold at the current descent rate (FIG. 4 ). The reference speed is faded up (117,118) at a rapid rate to 107% of rated speed (119). After a fixed time interval (129), reduce rotor loading (122), reduced pitch angle below a threshold magnitude (121) and reduced roll angle below a threshold magnitude (120) will cause the reference speed to be faded down slowly (146,147) to rated speed (148). Automatic increase in engine reference speed is overridden to 107% of rated speed (203) when a battle switch is activated (201) and weapons are ready (202). Increases in engine reference speed are prohibited (207) when the helicopter is operating in quiet mode (206) or the helicopter is resting on its wheels (208).
REFERENCES:
patent: 4488235 (1984-12-01), Miller
patent: 4807129 (1989-02-01), Perks
patent: 4947334 (1990-08-01), Massey et al.
patent: 4980684 (1990-12-01), Patterson et al.
patent: 4998202 (1991-03-01), Walsh et al.
patent: 5001646 (1991-03-01), Caldwell
patent: 5079711 (1992-01-01), Lambregts et al.
Ebert Frederick J.
Rice Robert W.
Ansley Virna Lissi
Grillo Michael
Huppert Michael S.
United Technologies Corporation
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